CN106828933B - A kind of high altitude long time tandem rotor aircraft aerodynamic arrangement using upper inverted diherdral difference - Google Patents
A kind of high altitude long time tandem rotor aircraft aerodynamic arrangement using upper inverted diherdral difference Download PDFInfo
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- CN106828933B CN106828933B CN201710074198.1A CN201710074198A CN106828933B CN 106828933 B CN106828933 B CN 106828933B CN 201710074198 A CN201710074198 A CN 201710074198A CN 106828933 B CN106828933 B CN 106828933B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/08—Aircraft not otherwise provided for having multiple wings
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Abstract
The invention discloses a kind of high altitude long time tandem rotor aircraft aerodynamic arrangements using upper inverted diherdral difference, belong to aerodynamic configuration of aircraft design field.In the aerodynamic configuration of aircraft, aircraft uses cylindrical cross-section fuselage, the front wing compared with high aspect ratio and rear wing, " V " type tail, wherein front wing is high mounted wing, and has the upper counterangle, is symmetrically mounted on fuselage front half section；Rear wing is lower single-blade, and has inverted diherdral, is symmetrically mounted on the fuselage second half section；" V " type tail is two, is symmetrically mounted on the fuselage second half section, and the upper counterangle is 45 °；Fanjet is mounted on above afterbody.The present invention can be used smaller length, improve structure efficiency under the premise of guaranteeing identical wing area, reduce the requirement to airport landing condition, and enhancing battlefield surroundings use ability；Front wing uses larger chord length, and rear wing uses smaller chord length, makes full use of advantageous interference of the rear wing to front wing, reduces unfavorable interference of the front wing to rear wing.
Description
Technical field
The invention belongs to aerodynamic configuration of aircraft design fields, and in particular to a kind of front and back wing is using upper inverted diherdral difference
High altitude long time tandem rotor aircraft aerodynamic arrangement.
Background technique
High altitude long time aircraft can complete long-range scouting, targeted surveillance, communication relay, electronic interferences, high Nuisance alarms
Equal military missions are the bases for constructing high-altitude strategy and tactics platform, have important strategy and tactics meaning.But high altitude long time
Aircraft is more demanding to flying quality, pneumatic quality etc., especially requires under the premise of enough lift, has larger
Lift resistance ratio.
For the Fixed Wing AirVehicle of subsonic speed normal arrangement, in design in order to obtain higher lift resistance ratio, by
In wing be its main lift member, thus would generally using increase wing aspect ratio method.High aspect ratio wing it is excellent
Point is: when vehicle flight speeds are lower, for the wing with same lift face area, the bigger aspect ratio of use has
Conducive to the induced drag for reducing wing, to obtain higher lift resistance ratio.
However, the length of wing compares machine since high altitude long time aircraft generallys use super large aspect ratio, big length wing
The thickness and chord length of the wing are much greater, thus may there is a problem of rigidity of structure deficiency.In flight course, wing can be
Flexible deformation occurs under the action of aerodynamic force, this flexible deformation changes correspondingly aerodynamic force again in turn, due to wing rigidity
Deficiency, easily form malformation and the interactive aeroelasticity phenomenon of aerodynamic force.Peace of the aeroelasticity phenomenon to aircraft
Complete and performance has considerable influence, can reduce driving efficiency, airfoil lift coefficient slope, in some instances it may even be possible in flight envelope
Within generate fulminant flutter, diverging, or even cause structure to damage suddenly and cause aircraft accident.To solve this problem, if
The mode for reinforcing wing rigidity is directlyed adopt, then the construction weight of wing can be made to greatly increase, reduce the effective of entire aircraft
Load and structure efficiency.
To meet the requirement that high altitude long time aircraft has enough lift, there is a kind of tandem wing aerodynamic arrangement cloth
Office includes former and later two wings, and rear wing can generate advantageous interference to front wing, however front wing can generate unfavorable interference to rear wing.This
Outside, when the whole angle of attack changes, interplane aerodynamic interference intensity is changed, so that each wing lift increment proportional will not change, leads
It causes the pneumatic focus moving range of full machine larger, influences flying quality.It flies in order to which tandem wing layout is applied to high altitude long time
Device aerodynamic arrangement also needs the influence to its structure parameters to aerodynamic characteristic to further investigate, a kind of optional pneumatic to obtain
Placement scheme.
Summary of the invention
The present invention from pneumatic design angle, deeply ground by the aerodynamic interference being laid out between the wing of front and back to the tandem wing
Study carefully, proposes the high altitude long time tandem rotor aircraft aerodynamic arrangement of inverted diherdral difference on a kind of wing of use front and back, provide one
Kind of structural behaviour and all good high altitude long time Flight Vehicle Design technical solution of aeroperformance.
Studies have shown that inverted diherdral difference can effectively improve unfavorable induction of the front wing wingtip vortex to rear wing aeroperformance on the wing of front and back
Effect is conducive to promote the whole aeroperformance of double-vane face layout；There is advantageous interference to front wing in rear wing, and front wing deposits rear wing
Effect is washed under induction；Rear wing using smaller chord length can weaken front wing it is unfavorable to rear wing under wash inductive effect.
Therefore, aerodynamic configuration of aircraft front wing of the present invention is larger chord length high mounted wing and has certain upper counterangle, rear wing be compared with
Single-blade and there is certain inverted diherdral under small chord length.Afterbody is disposed with engine and " V " type tail.
In the aerodynamic configuration of aircraft provided by the invention, aircraft uses cylindrical cross-section fuselage, larger exhibition string
Front wing and rear wing, " V " type tail of ratio, wherein front wing is high mounted wing, and has the upper counterangle, is symmetrically mounted on fuselage front half section；Afterwards
The wing is lower single-blade, and has inverted diherdral, is symmetrically mounted on the fuselage second half section；" V " type tail is two, and it is later half to be symmetrically mounted on fuselage
Section, the upper counterangle are 45 °；Fanjet is mounted on above afterbody.
The advantages of aerodynamic configuration of aircraft of the present invention, is:
(1) under the premise of guaranteeing identical wing area, smaller length can be used, improve structure efficiency, reduce pair
The requirement of airport landing condition, enhancing battlefield surroundings use ability.
(2) using bigger wing area is possessed when being laid out identical length and aspect ratio with single-blade, help to be promoted pneumatic
Performance increases high-altitude flight height, improves survival ability.
(3) poor using inverted diherdral on rear wing, front wing is reduced to the unfavorable disturbing effect of rear wing, is conducive to improve double-vane face
The whole aerodynamic characteristic of layout, so that the lift resistance ratio of aircraft meets or exceeds conventional single-blade face layout.
(4) front wing uses larger chord length, and rear wing uses smaller chord length, rear wing is made full use of to subtract the advantageous interference of front wing
Few unfavorable interference of the front wing to rear wing.
Detailed description of the invention
Fig. 1 is aerodynamic configuration of aircraft overall schematic of the present invention.
Fig. 2 is aerodynamic configuration of aircraft overall top view of the present invention.
Fig. 3 is aerodynamic configuration of aircraft entirety side view of the present invention.
Fig. 4 is aerodynamic configuration of aircraft entirety front view of the present invention.
Fig. 5 is that aerodynamic configuration of aircraft of the present invention compares common tandem wing layout lift resistance ratio with angle of attack variation curve graph.
In figure:
1. fuselage；2. front wing；3. rear wing；4. wing flap；5. aileron；6. engine；" 7. V " tail stabilization 8. " V " tail vane
Face.
Specific embodiment
The present invention is described further below with reference to attached drawing.
In aerodynamic configuration of aircraft of the present invention, aircraft uses cylindrical cross-section fuselage 1,2 and of front wing compared with high aspect ratio
Rear wing 3, " V " type tail, as shown in figures 1-4.Wherein, front wing 2 is the biggish high mounted wing of chord length, and has certain upper counterangle, symmetrically
It is mounted on fuselage front half section；Rear wing 3 is the lesser lower single-blade of chord length, and has certain inverted diherdral, is symmetrically mounted on the fuselage second half section；
" V " type tail is two, is symmetrically mounted on the fuselage second half section, and the upper counterangle is 45 °；Fanjet 6 is mounted on 1 tail portion of fuselage
Side.The chord length of the front wing 2 is greater than the chord length of the rear wing 3.The upper counterangle of the front wing 2 is 5 °, the upper counterangle of the rear wing 3
It is 5 °.
Such as Fig. 1 and Fig. 2,2 rear of front wing arranges wing flap 4 and aileron 5, and aileron 5 is to control aircraft rolling；" V " type tail
The wing includes " V " tail stabilization 7 and " V " the tail vane face 8 for being arranged in rear, and " V " tail stabilization 7 is to guarantee aircraft pitching and side
To stability, " V " tail vane face 8 is to control aircraft pitching and yaw.
The particularly inverted diherdral difference of the front wing 2 and rear wing 3 and aircraft entirety aeroperformance are closely related, need to be according to gas
The requirement of dynamic design determines.According to interplane interference mechanism, there is advantageous interference to front wing 2 in rear wing 3, and front wing 2 has rear wing 3
Effect is washed under induction.Therefore, it on the one hand needs on the other hand to need to the greatest extent as far as possible using advantageous interference of the rear wing 3 to front wing 2
The possible unfavorable interference for weakening front wing 2 to rear wing 3.Therefore, it is necessary to the different values of upper inverted diherdral difference to front and back wing to generate
Influence analyzed.
Embodiment: Fig. 5 gives of the invention be laid out on front wing 2 under anti-5 ° of rear wings 3 and is laid out in contrast to the common tandem wing for anti-5 °
Whole lift resistance ratio is with the three dimensional analysis curve of angle of attack variation, and ordinate LDR is lift resistance ratio, and abscissa AOA is the angle of attack, fp5-bp-5
For 5 ° of layouts anti-under 5 ° of rear wings 3 anti-on front wing 2 of the invention, h0c-3D is common tandem wing layout, wherein each wing uses
NACA4412 aerofoil profile, mean chord are 0.75m, aspect ratio 26.7.As can be seen that when the front and back wing being laid out in the present invention
When taking properly upper inverted diherdral difference, it can effectively improve front wing wingtip vortex to the unfavorable inductive effect of rear wing aeroperformance, be conducive to mention
Rise the whole aeroperformance of double-vane face layout.This illustrates that the present invention uses the aerodynamic arrangement of inverted diherdral difference on the wing of front and back to set rationally
Timing, which can be obtained, has more preferably pneumatic efficiency than common tandem rotor aircraft, is able to satisfy the use of high altitude long time aircraft
It is required that.
Claims (1)
1. a kind of high altitude long time tandem rotor aircraft aerodynamic arrangement using upper inverted diherdral difference, it is characterised in that: described flies
In Hang Qi aerodynamic arrangement, aircraft uses cylindrical cross-section fuselage, the front wing compared with high aspect ratio and rear wing, " V " type tail,
In, front wing is high mounted wing, and has the upper counterangle, is symmetrically mounted on fuselage front half section；Rear wing is lower single-blade, and has inverted diherdral, symmetrically
It is mounted on the fuselage second half section；" V " type tail is two, is symmetrically mounted on the fuselage second half section, and the upper counterangle is 45 °；Engine installation
Above afterbody；
The chord length of the front wing is greater than the chord length of the rear wing；
Front wing rear arranges wing flap and aileron, and aileron is to control aircraft rolling；" V " type tail include " V " tail stabilization and
Be arranged in " V " the tail vane face of rear, " V " tail stabilization to guarantee aircraft pitching and directional stability, " V " tail vane face to
Control aircraft pitching and yaw.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710074198.1A CN106828933B (en) | 2017-02-10 | 2017-02-10 | A kind of high altitude long time tandem rotor aircraft aerodynamic arrangement using upper inverted diherdral difference |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710074198.1A CN106828933B (en) | 2017-02-10 | 2017-02-10 | A kind of high altitude long time tandem rotor aircraft aerodynamic arrangement using upper inverted diherdral difference |
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| Publication Number | Publication Date |
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| CN106828933A CN106828933A (en) | 2017-06-13 |
| CN106828933B true CN106828933B (en) | 2019-06-18 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109598025B (en) * | 2018-11-02 | 2023-05-26 | 中国航空工业集团公司西安飞机设计研究所 | Optimal design method for inclination angle and area of V-shaped tail wing |
| CN110104160B (en) * | 2019-04-24 | 2021-01-01 | 北京航空航天大学 | Middle-distance coupling folding double-wing aircraft |
| CN111498085A (en) * | 2020-04-15 | 2020-08-07 | 成都飞机工业（集团）有限责任公司 | High-altitude long-endurance unmanned aerial vehicle wing suitable for lower single-wing layout |
| CN112644686B (en) * | 2020-12-25 | 2023-03-24 | 中国航天空气动力技术研究院 | Tandem wing overall arrangement solar energy unmanned aerial vehicle |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB302277A (en) * | 1927-12-13 | 1929-12-24 | Jacques Gerin | Improvements in airplanes having a variable lifting surface |
| US4365773A (en) * | 1979-04-11 | 1982-12-28 | Julian Wolkovitch | Joined wing aircraft |
| US4390150A (en) * | 1976-01-13 | 1983-06-28 | The Boeing Company | Tandem wing airplane |
| CN204399478U (en) * | 2014-12-04 | 2015-06-17 | 天津全华时代航天科技发展有限公司 | A kind of tandem wing formula unmanned plane |
-
2017
- 2017-02-10 CN CN201710074198.1A patent/CN106828933B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB302277A (en) * | 1927-12-13 | 1929-12-24 | Jacques Gerin | Improvements in airplanes having a variable lifting surface |
| US4390150A (en) * | 1976-01-13 | 1983-06-28 | The Boeing Company | Tandem wing airplane |
| US4365773A (en) * | 1979-04-11 | 1982-12-28 | Julian Wolkovitch | Joined wing aircraft |
| CN204399478U (en) * | 2014-12-04 | 2015-06-17 | 天津全华时代航天科技发展有限公司 | A kind of tandem wing formula unmanned plane |
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| CN106828933A (en) | 2017-06-13 |
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